Patent application title: SYSTEMS AND METHODS FOR BORESIGHT ADAPTERS

Abstract:

Boresighting systems and methods are disclosed. In one embodiment, an
assembly adapted for boresighting a launch system includes first and
second elongated members adapted to be coupled to the launch system.
First and second alignment members are coupled to and extend between the
first and second elongated members and are adapted to position the
elongated members in a substantially aligned, spaced-apart relationship.
A mirror assembly is coupled to each elongated member, the mirror
assemblies being adapted to provide an average angular position resulting
in a single corrector value for the launch system. In a particular
embodiment, each of the first and second elongated members is sized to
simulate a Stinger missile.

Claims:

1. An assembly adapted for boresighting a launch system, comprising:a
measurement system having a processor;first and second elongated members
configured to be coupled to the launch system;first and second alignment
members coupled to and extending between the first and second elongated
members and configured to position the elongated members in a
substantially aligned, spaced-apart relationship; anda mirror assembly
coupled to each elongated member, the mirror assemblies being configured
to provide input to the processor, the processor being configured to
determine, based on the input, an average angular position resulting in a
single corrector value for the launch system, wherein the single
corrector value is provided to the launch system for boresighting the
launch system.

2. The assembly of claim 1, wherein each of the first and second elongated
members includes a substantially-cylindrical body having a plurality of
interface locations configured to be coupled to the launch system.

3. The assembly of claim 2, wherein at least one interface location
comprises an annular band having a relatively larger diameter than a
diameter of an adjacent portion of the substantially-cylindrical body.

4. The assembly of claim 1, wherein each alignment member includes an
enlarged end coupled to a first one of the elongated members and a
cylindrical end coupled to another of the elongated members.

5. The assembly of claim 1, wherein each mirror assembly includes a first
mirror facing a first direction that is substantially parallel with a
longitudinal axis of its associated elongated member, and a second mirror
facing a second direction that is not parallel with the longitudinal
axis.

6. The assembly of claim 5, wherein the first direction intersects the
second direction.

7. A missile launch system, comprising:a base configured to be coupled to
a launch platform, the based having a plurality of attachment devices
configured to be coupled to at least one missile;an adapter assembly for
sighting the base, the adapter assembly including:a measurement system
having a processor; p2 first and second elongated members configured to
be coupled to the attachment devices of the base;first and second
alignment members coupled to and extending between the first and second
elongated members and configured to position the elongated members in a
substantially aligned, spaced-apart relationship; anda mirror assembly
coupled to each elongated member, the mirror assemblies being configured
to provide input to the processor, the processor being configured to
determine, based on the input, an average angular position resulting in a
single corrector value for the missile launch system, wherein the single
corrector value is provided to the launch system for boresighting the
launch system.

8. The system of claim 7, wherein each of the first and second elongated
members includes a substantially-cylindrical body having a plurality of
interface locations configured to be coupled to the launch system.

9. The system of claim 8, wherein at least one interface location
comprises an annular band having a relatively larger diameter than a
diameter of an adjacent portion of the substantially-cylindrical body.

10. The system of claim 7, wherein each alignment member includes an
enlarged end coupled to a first one of the elongated members and a
cylindrical end coupled to another of the elongated members.

11. The system of claim 7, wherein each mirror assembly includes a first
mirror facing a first direction that is substantially parallel with a
longitudinal axis of its associated elongated member, and a second mirror
facing a second direction that is not parallel with the longitudinal
axis.

12. The system of claim 11, wherein the first direction intersects the
second direction.

13. A method of sighting a launch system, comprising:engaging a first tube
member of an adapter assembly with the launch system;engaging a second
tube member of the adapter assembly with the launch system;adjusting a
first position of the first tube member relative to the second tube
member;securing the first tube member into the first position with
respect to the launch system;adjusting a second position of the second
tube member relative to the first tube member;securing the second tube
member into the second position with respect to the launch
system;performing measurements of at least one of the first and second
positions;determining a corrector value based on the measurements of the
at least one of the first and second positions; andboresighting the
launch system using the single corrector value.

14. The method of claim 13, wherein engaging a first tube member of an
adapter assembly with the launch system includes engaging an upper tube
member of an adapter assembly with the launch system.

15. The method of claim 13, wherein engaging a second tube member of an
adapter assembly with the launch system includes engaging an lower tube
member of an adapter assembly with the launch system.

16. The method of claim 13, wherein at least one of adjusting a first
position of the first tube member and adjusting a second position of the
second tube member includes adjusting a position of a one of the tube
members so that an end portion projecting outwardly from the one of the
tube members is positioned tangent to the other of the tube members.

17. The method of claim 13, wherein at least one of securing the first
tube member and securing the second tube member includes securing a
plurality of clamps of the launch system.

18. The method of claim 13, wherein performing measurements of at least
one of the first and second positions includes performing measurements of
both the first and second positions.

19. The method of claim 13, wherein performing measurements of at least
one of the first and second positions includes performing measurements of
at least one of an elevation value, an azimuth value, and a roll value.

20. The method of claim 13, wherein determining a corrector value based on
the measurements of the at least one of the first and second positions
includes at least one of averaging the measurements and comparing the
measurements with a predetermined value to determine the corrector value.

Description:

FIELD OF THE INVENTION

[0001]This invention relates to sighting systems, and more specifically,
to improved boresighting systems and methods for missile launchers and
other suitable devices.

BACKGROUND OF THE INVENTION

[0002]Many types of weapons systems require initial and periodic sighting
adjustment to ensure accurate operation. Missile launching systems, such
as those carried by aircraft, may require occasional sighting adjustment
to achieve the accuracy necessary to meet system specifications and
customer requirements. For example, the Air-to-Air Stinger missile
Launcher (ATAL) deployed on the AH-64D Apache helicopter requires a
boresighting procedure to accurately align the missile's seeker with the
helicopter's sighting system.

[0003]Although desirable results have been achieved using prior art
boresighting systems, there is room for improvement. For example, the
software of the AH-64D Apache allows only one boresight corrector per
wing pylon. The ATAL for the AH-64D, however, has two missiles, requiring
that the boresighting procedure be sequentially or iteratively performed,
with associated time and expense. Therefore, novel systems and methods
that would enable the accurate boresighting of two missiles
simultaneously would have utility.

SUMMARY OF THE INVENTION

[0004]The present invention is directed to improved boresighting systems
and methods for missile launchers and other suitable devices. Embodiments
of methods and systems in accordance with the present invention may
advantageously allow for boresighting of two devices simultaneously,
thereby improving the efficiency of the sighting process, and may also
improve the accuracy of the weapon system, in comparison with prior art
sighting systems.

[0005]In one embodiment, an assembly adapted for boresighting a launch
system includes first and second elongated members adapted to be coupled
to the launch system. First and second alignment members are coupled to
and extend between the first and second elongated members and are adapted
to position the elongated members in a substantially aligned,
spaced-apart relationship. A mirror assembly is coupled to each elongated
member, the mirror assemblies being adapted to provide an average angular
position resulting in a single corrector value for the launch system. In
a particular embodiment, each of the first and second elongated members
includes a substantially-cylindrical body having a plurality of interface
locations adapted to be coupled to the launch system, the elongated
members being adapted to simulate the size of a Stinger missile.

BRIEF DESCRIPTION OF THE DRAWINGS

[0006]Preferred and alternate embodiments of the present invention are
described in detail below with reference to the following drawings.

[0007]FIG. 1 is an isometric view of an adapter assembly in accordance
with an embodiment of the invention;

[0008]FIG. 2 is a partially-exploded top elevational view of the adapter
assembly of FIG. 1;

[0009]FIG. 3 is a top elevational view of a tube member of the adapter
assembly of FIG. 1;

[0010]FIG. 4 is a top elevational view of an alignment arm of the adapter
assembly of FIG. 1;

[0011]FIG. 5 is a front elevational view of first and second brackets of
the adapter assembly of FIG. 1;

[0012]FIG. 6 is an isometric view of the adapter assembly of FIG. 1
engaged with a missile launch system in accordance with another
embodiment of the invention;

[0013]FIG. 7 is a front isometric view of an aircraft having a plurality
of missile launch systems of FIG. 6 in accordance with another embodiment
of the invention; and

[0014]FIG. 8 is a flow diagram of a method of boresighting a launch system
in accordance with a further embodiment of the invention.

DETAILED DESCRIPTION

[0015]The present invention relates to improved boresighting systems and
methods for missiles and other suitable weapons systems. Many specific
details of certain embodiments of the invention are set forth in the
following description and in FIGS. 1-8 to provide a thorough
understanding of such embodiments. The present invention may have
additional embodiments, or may be practiced without one or more of the
details described for any particular described embodiment.

[0016]FIG. 1 is an isometric view of an adapter assembly 100 in accordance
with an embodiment of the invention. FIG. 2 is a partially-exploded top
elevational view of the adapter assembly 100 of FIG. 1. The adapter
assembly 100 includes a pair of tube members 110 and a pair of alignment
arms 120 that extend between the tube members 120, maintaining the tube
members 120 in a generally aligned relationship. In one particular
embodiment, the alignment arms 120 maintain the tube members 120 in an
approximately parallel relationship. A bracket 130 is coupled to a
forward end 116 of each of the tube members 110, and a mirror assembly
140 is attached to each of the brackets 130.

[0017]FIG. 3 is a top elevational view of one of the tube members 110 of
the adapter assembly 100 of FIG. 1. In this embodiment, the tube member
110 includes a cylindrical body 112 having a plurality of interface
locations 114. As described more fully below, the interface locations 114
are sized to engage with a corresponding plurality of attachment devices
of a launch system that is to be calibrated using the adapter assembly
100. As further shown in FIG. 3, a first seating location 111 is disposed
proximate a rearward end 113 of the tube member 110, and a second seating
location 115 is disposed proximate the forward end 116 of the tube member
110. As best shown in FIGS. 1 and 2, on the other tube member 110, the
locations of the first and second seating members 111, 113 are reversed.

[0018]FIG. 4 is a top elevational view of one of the alignment arms 120 of
the adapter assembly 100 of FIG. 1. In this embodiment, the alignment arm
120 includes an enlarged end 122 adapted to be coupled to the second
seating location 113 on the tube member 110 (FIGS. 1 and 2), and a
relatively smaller, cylindrical end portion 124 adapted to be coupled to
the first seating location 111 by a suitable coupling mechanism 126. In
the embodiment shown in FIGS. 1 and 2, the coupling mechanism 126
includes a hook member that engages over the cylindrical end portion 124,
clampably attaching the cylindrical end portion 124 to the tube member
110. In one presently preferred embodiment, the alignment arms 120 are
machined to tight tolerances and are rigidly secured to the tube members
110 to ensure that the mirror assemblies 140 (FIG. 1) are indexed
consistently from installation to installation.

[0019]FIG. 5 is a front elevational view of the brackets 130 of the
adapter assembly 100 of FIG. 1. Each bracket 130 includes a plurality of
first attachment locations 132 (e.g. apertures, threaded holes, etc.)
adapted for attaching the bracket 130 to the forward end 116 of the tube
member 110, and a plurality of second attachment locations 134 adapted
for attaching the corresponding mirror assembly 140 to the bracket 130
using, for example, threaded fasteners or other suitable attachment
mechanisms. As best shown in FIGS. 1 and 2, each mirror assembly 140
includes an angled support 142 that is coupled to the bracket 130, and
first and second mirrors 144, 146 coupled to the angled support 142. In
one particular embodiment, the mirror assembly 140 is a model that is
commercially-available from AAI Corporation of Hunt Valley, Md.

[0020]FIG. 6 is an isometric view of the adapter assembly 100 of FIG. 1
engaged with a missile launch system 200 in accordance with another
embodiment of the invention. In this embodiment, the missile launch
system 200 includes a base 210 that is adapted to be coupled an aircraft
or other suitable launch platform. A plurality of clamps 220 are engaged
with the interface locations 114 of the tube members 110, thereby
securing the adapter assembly 100 to the missile launch system 200. In
one particular embodiment, the missile launch system 200 may be the
Air-to-Air Stinger missile Launcher (ATAL) produced by the Raytheon
Company's Missile Systems division of Tucson, Arizona. Similarly, in one
particular embodiment, the adapter assembly 100, and in particular the
tube members 110, are sized and otherwise adapted to simulate the
Air-to-Air Stinger missile for purposes of properly boresighting the ATAL
missile launch system 200, as described more fully below.

[0021]The missile launch system 200 may be adapted to be coupled an
aircraft or other suitable launch platform. For example, FIG. 7 is a
front isometric view of an aircraft 300 having a plurality of missile
launch systems 200 of FIG. 6. The missile launch systems 200 may be
sighted using the adapter assembly 100 in accordance with the present
invention. In the embodiment shown in FIG. 7, the aircraft is an AH-64D
Apache helicopter. In alternate embodiments, however, the missile launch
systems 200 may be coupled to a variety of different launch platforms,
including, for example, the OH-58C, OH-58D, MH-60, AH-1Z, AH-64D, and
RAH-66 helicopters, as well as any other suitable manned and unmanned
aircraft.

[0022]FIG. 8 is a flow diagram of a method 800 of boresighting a launch
system in accordance with a further embodiment of the invention. In this
embodiment, the method 800 includes engaging a first tube member of an
adapter assembly (e.g. the upper tube member) with a launch system at a
block 802. For example, in the case of the ATAL missile launch system 200
(FIG. 6), the upper tube member of the adapter assembly 100 may be placed
into the three clamps 220. Similarly, at a block 804, a second tube
member (e.g. the lower tube member) is engaged with the launch system.
Next, a position of the first tube member is adjusted so that an end
portion of a first alignment arm (e.g. end portion 124 of the alignment
arm 120 of FIGS. 1-2) is tangent to the second tube member at a block
806. The first tube member is then secured into position on the launch
system at a block 808, such as, for example, by securely engaging the
clamps 220 of the launch system 200 (FIG. 6). Similarly, at a block 810,
a position of the second tube member is adjusted so that an end portion
of a second alignment arm is tangent to the first tube member, and the
second tube member is then secured into position on the launch system at
a block 812.

[0023]One or more measurements of the positions of the first and second
tube members may then be taken using any suitable boresighting
measurement system at a block 814. For example, in various embodiments,
the measurements may be obtained using a variety of systems, including,
for example, an Advanced Boresighting Equipment (ABE) system available
from United Industrial Corporation of Hunt Valley, Md., a Captive
Boresight Harmonization Kit (CBHK) available from DRS Technologies of
Parsippany, N.J., a Theodolite-based sighting system, or any other
suitable measurement systems. In one particular embodiment, measurements
of an elevation, azimuth, and roll position are taken for each of the
tube members. Finally, at a block 816, the measurements of the positions
of the first and second tube members are processed to determine a
corrector value for correcting a sighting of the launch system. In a
particular embodiment, the position measurements of the first and second
tube members are averaged and compared with predetermined desired or
calibration values to determine the corrector value, and the correcter
value is then provided into a processor of the launch system.

[0024]Embodiments of the present invention may provide significant
advantages over the prior art. For example, adapter assemblies in
accordance with the present invention improve the efficiency of the
boresighting process by creating an accurate physical representation of
the two missiles to create an average angular position resulting in a
single corrector value for the launch system. Thus, the time and expense
associated with boresighting the launch system may be considerably
reduced in comparison with prior art sighting procedures.

[0025]While preferred and alternate embodiments of the invention have been
illustrated and described, as noted above, many changes can be made
without departing from the spirit and scope of the invention.
Accordingly, the scope of the invention is not limited by the disclosure
of these preferred and alternate embodiments. Instead, the invention
should be determined entirely by reference to the claims that follow.